Systems and methods to improve shut-down purge flow in a gas turbine system

A system includes a controller including a memory storing instructions to perform operations of a power generation system and a processor that executes the instructions. The instructions cause the controller to control purging fluid flow to an inlet of a gas turbine, an exhaust of the gas turbine, or a combustion section of the gas turbine. The instructions cause the controller to receive a first temperature at the inlet, a rotational speed of the gas turbine, and a purging fluid flow rate. The instructions cause the controller to calculate an exhaust flow rate of the system based on at least the first temperature, the rotational speed, and the purging fluid flow rate. The instructions cause the controller to control the system to isolate a fuel source from the gas turbine at a portion of normal operating speed sufficient to achieve a purging volume during coast down.

Application of probabilistic control in gas turbine tuning for power output-emissions parameters with scaling factor, related control systems, computer program products and methods

Various embodiments include a system having: at least one computing device configured to tune a set of gas turbines (GTs) by performing actions including: commanding each GT in the set of GTs to a base load level, based upon a measured ambient condition for each GT; commanding each GT in the set of GTs to adjust a respective power output to match a scaled power output value equal to a fraction of a difference between the respective power output and a nominal power output value, and subsequently measuring an actual emissions value for each GT; and adjusting an operating condition of each GT in the set of GTs based upon a difference between the respective measured actual emissions value, a nominal emissions value at the ambient condition and a nominal emissions value at the ambient condition.

Application of combined probabilistic control in gas turbine tuning for power output-emissions parameters with scaling factor, related control systems, computer program products and methods

Various embodiments include a system having: at least one computing device configured to tune a set of gas turbines (GTs) by performing actions including: modelling each GT in the set of GTs at a base load level, based upon a measured ambient condition for each GT; commanding each GT in the set of GTs to adjust a respective power output to match a scaled power output value equal to a fraction of a difference between the respective power output and a nominal power output value, and measuring an actual emissions value for each GT during the adjusting of the respective power output; and adjusting an operating condition of each GT in the set of GTs based upon a difference between the respective measured actual emissions value, a nominal emissions value at the ambient condition and a nominal emissions value at the ambient condition.

Machine-specific combined probabilistic control in gas turbine tuning for power output-emissions parameters with scaling factor, related control systems, computer program products and methods

Commanding GTs to base load level based upon measured ambient condition for each GT; commanding each GT to adjust a power output to match scaled power output value equal to a fraction of a difference between the respective power output and a nominal power output value, and measuring actual emissions value for each GT during the adjusting of the respective power output; adjusting operating condition of each GT based upon a difference between the respective measured actual emissions value, a nominal emissions value at the ambient condition and emissions scale factor; updating a pre-existing emissions model for each GT based upon the adjusted operating; running set of operating conditions on each GT and measuring updated parameters for each GT including an updated emissions value; and refining updated pre-existing emissions model based upon a difference between the updated emissions value and the updated pre-existing emissions model.

Systems for reducing startup emissions in power plant including gas turbine

Embodiments of emission reduction system including various embodiments of an emission filters for a power plant including a gas turbine are disclosed. The system includes: an emission filter; and a retraction system operably coupled to an exhaust passage of the gas turbine. The exhaust passage defines an exhaust path of exhaust from the gas turbine. The retraction system selectively moves the emission filter between a first location within the exhaust path and a second location out of the exhaust path. In a combined cycle power plant, the first location is upstream of a heat recovery steam generator (HRSG). The systems and filters described allow for temporary positioning of emission filter(s) just downstream of a gas turbine exhaust outlet, or upstream of an HRSG, where provided, for emission reduction at low loads or startup conditions, and removal of the emission filter(s) once operations move to higher loads.

Application of probabilistic control in gas turbine tuning for exhaust energy-emissions parameters, related control systems, computer program products and methods

Various embodiments include a system having: at least one computing device configured to tune a set of gas turbines (GTs) by performing actions including: commanding each GT in the set of GTs to a base load level, based upon a measured ambient condition for each GT; commanding each GT in the set of GTs to adjust a respective exhaust energy to match a nominal exhaust energy value, and subsequently measuring an actual emissions value for each GT; and adjusting an operating condition of each GT in the set of GTs based upon a difference between the respective measured actual emissions value and a nominal emissions value at the ambient condition.

Application of probabilistic control in gas turbine tuning for exhaust energy-power output parameters, related control systems, computer program products and methods

Various embodiments include a system having: at least one computing device configured to tune a set of gas turbines (GTs) by performing actions including: commanding each GT in the set of GTs to a base load level, based upon a measured ambient condition for each GT; commanding each GT in the set of GTs to adjust a respective exhaust energy to match a nominal exhaust energy value, and subsequently measuring an actual power output value for each GT; and adjusting an operating condition of each GT in the set of GTs based upon a difference between the respective measured actual power output value and a nominal power output value at the ambient condition.

Application of probabilistic control in gas turbine tuning for emissions-fuel flow parameters, related control systems, computer program products and methods

Various embodiments include a system having: at least one computing device configured to tune a set of gas turbines (GTs) by performing actions including: commanding each GT in the set of GTs to a base load level, based upon a measured ambient condition for each GT; commanding each GT in the set of GTs to adjust a respective emissions value to match a nominal emissions value, and subsequently measuring an actual fuel flow value for each GT; and adjusting an operating condition of each GT in the set of GTs based upon a difference between the respective measured actual fuel flow value and a nominal fuel flow value at the ambient condition.

Application of probabilistic control in gas turbine tuning for fuel flow-exhaust energy parameters, related control systems, computer program products and methods

Various embodiments include a system having: at least one computing device configured to tune a set of gas turbines (GTs) by performing actions including: commanding each GT in the set of GTs to a base load level, based upon a measured ambient condition for each GT; commanding each GT in the set of GTs to adjust a respective fuel flow value to match a nominal fuel flow value, and subsequently measuring an actual exhaust energy value for each GT; and adjusting an operating condition of each GT in the set of GTs based upon a difference between the respective measured actual exhaust energy value and a nominal exhaust energy value at the ambient condition.

Power generation system exhaust cooling

An airflow control system control system for a gas turbine system according to an embodiment includes: an airflow generation system including a plurality of air moving systems for selective attachment to a rotatable shaft of a gas turbine system, the airflow generation system drawing in an excess flow of air through an air intake section; and a mixing area for receiving an exhaust gas stream of the gas turbine system; the airflow generation system: directing a first portion and a second portion of the excess flow of air generated by the airflow generation system into the mixing area to reduce a temperature of the exhaust gas stream; and directing a third portion of the excess flow of air generated by the airflow generation system into a discharge chamber of a compressor component of the gas turbine system.

Power generation system exhaust cooling

An airflow control system for a combined cycle power generation system according to an embodiment includes: a compressor component of a gas turbine system for generating an excess flow of air; a mixing area for receiving an exhaust gas stream produced by the gas turbine system; and an air extraction system for extracting at least a portion of the excess flow of air generated by the compressor component of the gas turbine system to provide bypass air, and for diverting the bypass air into the mixing area to reduce a temperature of the exhaust gas stream; wherein the reduced temperature exhaust gas stream is provided to a heat recovery steam generator.

Power generation system exhaust cooling

An airflow control system for a gas turbine according to an embodiment includes: an airflow generation system for attachment to a rotatable shaft of a gas turbine system, the airflow generation system drawing in an excess flow of air through an air intake section; a mixing area for receiving an exhaust gas stream of the gas turbine system; an air extraction system for: extracting at least a portion of the excess flow of air generated by the airflow generation system to provide bypass air; and diverting the bypass air into the mixing area to reduce a temperature of the exhaust gas stream; and an exhaust processing system for processing the reduced temperature exhaust gas stream.

Displaceable fuel nozzles in cap-less combustor assembly

A combustor (100, 300, 400) includes a central fuel nozzle assembly (304) and a plurality of outer fuel nozzle assemblies (308), each of the plurality of outer fuel nozzle assemblies (308) having a center body (310) and an outer shroud (312), the plurality of outer fuel nozzle assemblies (308) being configured to abut one another in a surrounding relationship to the central cylinder (304) such that no gaps are present between any two abutting ones of the plurality of outer fuel nozzle assemblies (308). One or more of the plurality of fuel nozzle assemblies (104, 304, 308) may traverse axially back and forth according to embodiments of the invention.

Combustor assembly for a turbine engine with enhanced cooling

A combustor assembly for a turbine engine includes a combustor liner and a flow sleeve which surrounds the combustor liner. Compressed air flows through an annular space located between an outer surface of the combustor liner and an inner surface of the flow sleeve. A plurality of cooling holes are formed through the flow sleeve to allow compressed air to flow from a position outside the flow sleeve, through the cooling holes, and into the annular space. The height of the annular space may vary along the length of the combustor assembly. Thus, the flow sleeve may have reduced diameter portions which result in the height of the annular space being smaller in certain locations than at other locations along the length of the combustor assembly.

System and method for barrier in passage of combustor of gas turbine engine with exhaust gas recirculation

In one embodiment, a system includes a turbine combustor having a combustor liner disposed about a combustion chamber, a head end upstream of the combustion chamber relative to a downstream direction of a flow of combustion gases through the combustion chamber, a flow sleeve disposed at an offset about the combustor liner to define a passage, and a barrier within the passage. The head end is configured to direct an oxidant flow and a first fuel flow toward the combustion chamber. The passage is configured to direct a gas flow toward the head end and to direct a portion of the oxidant flow toward a turbine end of the turbine combustor. The gas flow includes a substantially inert gas. The barrier is configured to block the portion of the oxidant flow toward the turbine end and to block the gas flow toward the head end within the passage.

System and method for controlling the combustion process in a gas turbine operating with exhaust gas recirculation

A system includes a fuel control system configured to control a fuel flow to one or more combustors and an oxidant control system configured to control an oxidant flow to each combustor of the one or more combustors, wherein the oxidant flow is configured to at least partially react with the fuel flow within the one or more combustors to form an exhaust gas flow. The system also includes an exhaust gas system configured to direct a recirculation flow of the exhaust gas flow to each combustor of the one or more combustors; and a controller coupled to the fuel control system, the oxidant control system, and the exhaust gas system. The controller is configured to independently control a fuel-to-oxidant ratio and an exhaust gas-to-oxidant ratio. The FOR is the fuel flow divided by the oxidant flow, and the EGOR is the recirculation flow divided by the oxidant flow.

Three-dimensional optical sensor and system for combustion sensing and control

A system includes an optical sensor that optically measures and spatially resolves in three dimensions at least one chemical species within a flame produced by a device and a component that correlates the three dimensionally measured at least one chemical species to at least one parameter of the device.

FLAME RETENTION REDUCTION FUSE IN A COMBUSTION CHAMBER PREMIXER OF A GAS TURBINE AND METHOD THEREFOR.

Ensemble de buse à combustible pour un brûleur d'une turbine à gaz, comprenant : un corps de buse (40) avec une partie avant et un tube intérieur (69) délimitant un canal de combustible (68) qui s'étend à travers le corps de buse, la partie avant se trouvant à proximité d'une section de combustion du brûleur; une enveloppe extérieure (78) disposée autour du tube intérieur, un canal d'air (76) étant défini entre l'enveloppe extérieure et le tube intérieur; une conduite de gaz (56) qui est agencée dans le canal d'air et comporte un orifice de sortie à proximité de la partie avant du corps de buse, le combustible commençant à s'écouler à travers la conduite dilatable, uniquement après la survenue d'une remontée de flamme dans le brûleur; et un canal de combustible de prémélange (70, 71) et un orifice (61, 62) distribuant le combustible à une section de prémélange du brûleur, la conduite de gaz ayant un orifice d'entrée s'ouvrant sur le canal de combustible de prémélange. A fuel nozzle assembly for a gas turbine burner, comprising: a nozzle body (40) with a front portion and an inner tube (69) defining a fuel channel (68) extending through the nozzle nozzle body, the front part being in the vicinity of a combustion section of the burner; an outer casing (78) disposed around the inner tube, an air channel (76) being defined between the outer casing and the inner tube; a gas line (56) which is arranged in the air channel and has an outlet port near the front part of the nozzle body, the fuel starting to flow through the expandable conduit only after the occurrence a rising flame in the burner; and a premix fuel channel (70, 71) and an orifice (61, 62) distributing the fuel to a burner premix section, the gas line having an inlet port opening to the burner fuel channel premix.

FUEL INJECTOR FOR RESISTANCE TO A FLAME RETENTION INCIDENT

Injecteur (1) comprenant un volume annulaire extérieur (10) défini par une paroi externe (11) et une paroi interne (12) et comportant des entrées d'air (80) par lesquelles l'air rejoint une zone de mélange (16) de combustible et une zone de combustion (50), un volume annulaire intérieur (20) disposé dans la paroi interne (12) et comportant un volume D pour combustible dans lequel du combustible est introduit jusqu'à une extrémité distale (23) de celui-ci, qui est adjacente à la zone de combustion (50) et est isolée de celle-ci, et une conduite de circulation d'air (40), disposée entre le volume D pour combustible et la paroi interne (12), par laquelle l'air rejoint la zone de combustion (50), la conduite de circulation d'air (40) et la zone de combustion (50) étant isolées du volume D pour combustible, et un fusible conçu pour fondre pendant un incident de retenue de flamme et pour créer une brèche par laquelle le combustible passe du volume D pour combustible, en évitant la zone de mélange (16) de combustible, à une zone de combustion (17) de combustible en aval de la zone de mélange (16) de combustible. Injector (1) comprising an outer annular space (10) defined by an outer wall (11) and an inner wall (12) and having air inlets (80) through which the air reaches a mixing zone (16) of fuel and a combustion zone (50), an inner annular volume (20) disposed in the inner wall (12) and having a fuel volume D in which fuel is introduced to a distal end (23) of the fuel adjacent to the combustion zone (50) and is isolated therefrom, and an air circulation duct (40) disposed between the fuel volume D and the inner wall (12), which air joins the combustion zone (50), the air circulation duct (40) and the combustion zone (50) being isolated from the fuel volume D, and a fuse designed to melt during a restraint incident flame and to create a gap through which the fuel passes volume D for fuel, while the fuel mixing zone (16) at a fuel combustion zone ( ...

Application of probabilistic control in gas turbine tuning for power output-emissions parameters, related control systems, computer program products and methods

Various embodiments include a system having: at least one computing device configured to tune a set of gas turbines (GTs) by performing actions including: commanding each GT in the set of GTs to a base load level, based upon a measured ambient condition for each GT; commanding each GT in the set of GTs to adjust a respective power output to match a nominal power output value, and subsequently measuring an actual emissions value for each GT; and adjusting an operating condition of each GT in the set of GTs based upon a difference between the respective measured actual emissions value and a nominal emissions value at the ambient condition.

Application of combined probabilistic control in gas turbine tuning for power output-emissions parameters with scaling factor, related control systems, computer program products and methods

Various embodiments include a system having: at least one computing device configured to tune a set of gas turbines (GTs) by performing actions including: commanding P1 each GT in the set of GTs to a base load level, based upon a measured ambient condition for each GT; commanding P2 each GT in the set of GTs to adjust a respective power output to match a scaled power output value equal to a fraction of a difference between the respective power output and a nominal power output value, and modeling an emissions value for the GT during the adjusting of the respective power output; and adjusting P3 an operating condition of each GT in the set of GTs based upon a difference between the respective modelled emissions value, a nominal emissions value at the ambient condition and a nominal emissions value at the ambient condition.

Fuel trim system for a combustion system in a multi-combustion gas turbine

Fuel control and tuning method for dry low NOx gas turbine engines

Systems and methods for controlling compressor extraction cooling

Embodiments of methods and apparatus for providing compressor extraction cooling are provided. According to one example embodiment, a method is disclosed for controlling compressor extraction cooling. The method can include providing a cooling medium. The method can include extracting air from a compressor associated with a gas turbine. The method can also include introducing the cooling medium to the compressor extraction air, wherein the compressor extraction air is cooled by the cooling medium prior to or during introduction to the turbine section. Furthermore, method can include selectively controlling at least one of the compressor extraction air or the cooling medium based at least in part on a characteristic associated with the gas turbine.

Use of fuel flow-based probability control in the setting of gas turbines under part load, related control systems, computer program products and methods

Verschiedene Ausführungsbeispiele enthalten ein System (18) mit: Zumindest einer Recheneinrichtung (814), die dazu eingerichtet ist, einen Satz von Gasturbinen (GTs (10)) durch Ausführen von Aktionen einzustellen, aufweisend: Befehlen jeder GT (10) in dem Satz von GTs (10) auf ein Basislastniveau, basierend auf einem gemessenen Umgebungszustand für jede GT (10); Befehlen jeder GT (10) in dem Satz von GTs (10) zum Einstellen einer jeweiligen Ausgangsleistung, um mit einem nominellen Megawatt-Leistungsausgangswert übereinzustimmen und anschließend messen eines aktuellen Brennstoffströmungswertes für jede GT (10); Einstellen eines Betriebszustandes für jede GT (10) in dem Satz von GTs (10) basierend auf einer Differenz zwischen dem jeweils gemessenen aktuellen Brennstoffströmungswert und einem nominellen Brennstoffströmungswert bei dem Umgebungszustand; Befehlen jeder GT (10) in dem Satz von GTs (10) auf ein Teillastniveau, wobei das Teillastniveau einen Bruchteil des Basislastniveaus darstellt und anschließend messen eines aktuellen Brennstoffströmungswertes für jede GT (10) bei dem Teillastniveau; und Kalibrieren des Satzes von GTs (10) basierend auf einer Differenz zwischen dem gemessenen aktuellen Brennstoffströmungswert bei dem Teillastniveau und dem gemessenen aktuellen Brennstoffströmungswert nach dem Einstellen der Ausgangsleistung, um diese in Übereinstimmung mit dem nominellen Megawatt-Leistungsausgangswert zu bringen. Various embodiments include a system (18) comprising: at least one computing device (814) configured to set a set of gas turbines (GTs (10)) by performing actions, comprising: commanding each GT (10) in the set of GTs (10) to a base load level based on a measured environmental condition for each GT (10); Commanding each GT (10) in the set of GTs (10) to set a respective output power to coincide with a nominal megawatt power output value and then measuring a current fuel flow value for each GT (10); Setting an operating condition for each GT (10 ...

System and method for controlling the combustion process in a gas turbine operating with exhaust gas recirculation

Application of combined probabilistic control in gas turbine tuning for power output-emissions parameters with scaling factor, related control systems, computer program products and methods

Various embodiments include a system having: at least one computing device configured to tune a set of gas turbines (GTs) by performing actions including: modelling each GT in the set of GTs at a base load level, based upon a measured ambient condition for each GT; commanding each GT in the set of GTs to adjust a respective power output to match a scaled power output value equal to a fraction of a difference between the respective power output and a nominal power output value, and measuring an actual emissions value for each GT during the adjusting of the respective power output; and adjusting an operating condition of each GT in the set of GTs based upon a difference between the respective measured actual emissions value, a nominal emissions value at the ambient condition and a nominal emissions value at the ambient condition.

Application of probabilistic control in gas turbine tuning for emissions-exhaust energy parameters, related control systems, computer program products and methods

Various embodiments include a system having: at least one computing device configured to tune a set of gas turbines (GTs) by performing actions including: commanding each GT in the set of GTs to a base load level, based upon a measured ambient condition for each GT; commanding each GT in the set of GTs to adjust a respective emissions value to match a nominal emissions value, and subsequently measuring an actual exhaust energy value for each GT; and adjusting an operating condition of each GT in the set of GTs based upon a difference between the respective measured actual exhaust energy value and a nominal exhaust energy value at the ambient condition.

Combustor liner

A combustor within which a combustion zone is defined is provided and includes an annular liner having a first mixing hole defined therein at a first axial position, a flow sleeve, having a second mixing hole defined therein at a second axial position, the flow sleeve surrounding the liner to form a first flow space at an exterior of the liner, a port, coupled to the flow sleeve at the second axial position, which is configured to remove air from the first flow space via the second mixing hole, and a shield, having a third mixing hole defined therein at the second axial position, the shield being disposed to shield the liner and to form a second flow space within the liner, which is communicable with the combustion zone via the third mixing hole and with the first flow space via the first mixing hole.

Three-dimensional optical sensor and system for combustion sensing and control

A system includes an optical sensor that optically measures and spatially resolves in three dimensions at least one chemical species within a flame produced by a device and a component that correlates the three dimensionally measured at least one chemical species to at least one parameter of the device.

Thermally decoupled can-annular transition piece

A turbomachine includes a plurality of injection nozzles arranged in a can-annular array and a transition piece including at least one wall that defines a combustion flow passage. A dilution orifice is formed in the at least one wall of the transition piece. The dilution orifice guides dilution gases to the combustion flow passage. A heat shield member is mounted to the at least one wall of the transition piece in the combustion flow passage. The heat shield member includes a body having a first surface and an opposing second surface through which extends a dilution passage. The dilution passage is off-set from the dilution orifice. The heat shield member is spaced from the at least one wall of the transition piece defining a flow region between the at least one wall and the second surface.

Thermally decoupled can-annular transition piece

Power generation system having compressor creating excess air flow for scr unit

A power generation system (100) includes a turbine component (104), an integral compressor (106) and a combustor (108) to which air from the integral compressor and fuel are supplied, the integral compressor having a flow capacity greater than an intake capacity of at least one of the combustor and the turbine component, creating an excess air flow (200). A first control valve system (202) controls flow of the excess air flow (200) along an excess air flow path (250) to an exhaust (172) of the turbine component (104). A selective catalytic reduction (SCR) unit (168) may be coupled to an exhaust (172) of the turbine component, the SCR unit receiving the exhaust and the excess air flow. An eductor (252) may be positioned in the excess air flow path (250) for using the excess air flow as a motive force to augment the excess air flow with additional air (254).

Systems and methods for gas turbine tuning and control

A method of tuning a gas turbine includes receiving a first plurality of operating parameters as the gas turbine engine is operated at a first operating state. Further, the method includes operating the gas turbine engine at a second operating state to measure a second plurality of operating parameters at the second operating state. In addition, the method includes operating the gas turbine engine at a third operating state to measure a third plurality of operating parameters at the third operating state, wherein the first, second, and third operating states are different from each other. Additionally, the method includes generating a correction factor based on the first, second, and third plurality of operating parameters. The method also includes adjusting the operation of the gas turbine engine based on the correction factor.

Catalytically Stabilized Gas Turbine Combustor

A gas turbine combustor. The gas turbine combustor may include a central combustion nozzle with a catalyst therein and a number of outer combustion nozzles surrounding the central combustion nozzle.

Late lean injection with expanded fuel flexibility

A gas turbine engine (10) is provided and includes a fuel circuit (70), including multiple fuel circuit branches (71, 72), a combustor (20) having a first interior (21) in which a first fuel supplied thereto by any one of the multiple fuel circuit branches (71, 72) is combustible, a turbine (50), a transition zone (43), including a second interior (41) in which a second fuel supplied thereto by any one of the multiple fuel circuit branches (71, 72). The second fuel includes gas receivable by the fuel circuit (70) from an external source, and the products of the combustion of the first fuel are combustible, the transition zone (43) being disposed to fluidly couple the combustor (20) and the turbine (50) to one another. A plurality of fuel injectors (60) supply the second fuel to the second interior (41) in any one of a single axial stage, multiple axial stages, a single axial circumferential stage and multiple axial circumferential stages.

Tertiary fuel injection system for use in a dry low nox combustion system

An improved gas turbine combustor of the type including primary and secondary combustion chambers with a venturi including a throat portion located therebetween; a plurality of primary fuel infection nozzles secured to a combustor cap an an annular array upstream of the primary combustion chamber; and a centerbody including a secondary fuel nozzle, said centerbody extending from said combustor cap to said secondary combustion chamber; the improvement comprising a plurality of tertiary foal injection nozzles arranged in a circular array about a longitudinal axis of the combustor, at a downstream of said venturi throat portion, for injecting fuel into the secondary combustion chamber.

Airflow control system of a gas turbine for exhaust cooling

Method of trimming fuel supply in a gas turbine, as well as such gas turbine

Power generation system exhaust cooling

A system for reducing a temperature of an exhaust gas stream of a gas turbine system according to an embodiment includes: a compressor component of a gas turbine system; an airflow generation system for attachment to a rotatable shaft of the gas turbine system, the airflow generation system and the compressor component drawing in an excess flow of air through an air intake section; a mixing area for receiving an exhaust gas stream produced by the gas turbine system; an air extraction system for: extracting at least a portion of the excess flow of air generated by the airflow generation system and the compressor component to provide bypass air; and diverting the bypass air into the mixing area to reduce a temperature of the exhaust gas stream; and a fluid injection system for injecting an atomized fluid into the mixing area to reduce a temperature of the exhaust gas stream.

Optical interrogation sensors for combustion control

Certain embodiments of the invention may include systems and methods for providing optical interrogation sensors for combustion control. According to an example embodiment of the invention, a method for controlling combustion parameters associated with a gas turbine combustor is provided. The method can include providing an optical path through the gas turbine combustor, propagating light along the optical path, measuring absorption of the light within the gas turbine combustor, and controlling at least one of the combustion parameters based at least in part on the measured absorption.

Combustor assembly for a turbine engine with enhanced cooling

A combustor assembly for a turbine engine includes a combustor liner and a flow sleeve which surrounds the combustor liner. Compressed air flows through an annular space located between an outer surface of the combustor liner and an inner surface of the flow sleeve. A plurality of cooling holes are formed through the flow sleeve to allow compressed air to flow from a position outside the flow sleeve, through the cooling holes, and into the annular space. The height of the annular space may vary along the length of the combustor assembly. Thus, the flow sleeve may have reduced diameter portions which result in the height of the annular space being smaller in certain locations than at other locations along the length of the combustor assembly.

System and method of controlling combustion and emissions in gas turbine engine with exhaust gas recirculation

Burner for a gas turbine with several tubular combustion chambers and several resonators.

Ein Brenner für eine Gasturbine und ein zugehöriges Verfahren werden bereitgestellt, in welchen mehrere Rohrbrennkammern (26) selektiv mit entsprechenden Resonatoren angepasst werden. Die Resonatoren können beispielsweise an jedem Rohr in der aufeinanderfolgenden Anordnung von Rohrbrennkammern, jedem zweiten Rohr (400–416), jedem dritten Rohr oder dergleichen angebracht werden und können auf dieselbe oder erste, zweite, dritte usw. Betriebsfrequenz abgestimmt werden. Insbesondere sind die Resonatoren (400–416, 500–534, 600–612) selektiv so abgestimmt, dass sich Instabilitätsfrequenzen in jeder Rohrbrennkammer (26) von den Instabilitätsfrequenzen der benachbarten Rohrbrennkammern unterscheiden. Eine derartige selektive Abstimmung ist dafür konfiguriert, eine oder mehrere gegenphasige oder gleichphasige dynamische Wechselwirkungen von aus benachbarten Rohrbrennkammern ausgegebenen Strömen zu unterdrücken, indem die Frequenzen von Druckoszillationsinstabilitäten über der Anordnung aufeinanderfolgender Rohre verändert werden. A gas turbine combustor and associated method are provided in which a plurality of tube combustors (26) are selectively matched to corresponding resonators. For example, the resonators may be mounted on each tube in the sequential arrangement of tube combustors, every other tube (400-416), every third tube, or the like, and may be tuned to the same or first, second, third, etc. operating frequency. In particular, the resonators (400-416, 500-534, 600-612) are selectively tuned so that instability frequencies in each tube combustion chamber (26) are different from the instability frequencies of the adjacent tube combustion chambers. Such selective tuning is configured to suppress one or more out of phase or in-phase dynamic interactions of currents output from adjacent tube combustors by varying the frequencies of pressure oscillation instabilities across the array of successive tubes.

Traversing fuel nozzles in cap-less combustor assembly

A combustor includes a central fuel nozzle assembly and a plurality of outer fuel nozzle assemblies, each of the plurality of outer fuel nozzle assemblies having a center body and an outer shroud, the plurality of outer fuel nozzle assemblies being configured to abut one another in a surrounding relationship to the central cylinder such that no gaps are present between any two abutting ones of the plurality of outer fuel nozzle assemblies. One or more of the plurality of fuel nozzle assemblies may traverse axially back and forth according to embodiments of the invention.

Methods and Systems for Controlling a Combustor in Turbine Engines

Embodiments of methods and systems for controlling a combustor for a gas turbine engine are provided. According to one example embodiment, a system includes an air control assembly associated with at least one air path of a combustor for a gas turbine engine. Additionally, the system also includes at least one sensor for sensing at least one operating parameter of the gas turbine engine. Further, the system also includes a controller operable to receive at least one operating parameter sensed by the at least one sensor, and further operable to selectively control an air control assembly based at least in part on the at least one operating parameter sensed by the at least one sensor.

Late lean injection control strategy

A gas turbine engine (10) is provided and includes a combustor (20) having a first interior (21) in which a first fuel supplied thereto by a fuel circuit (70) is combustible, a turbine (50), a transition zone (43), including a second interior (41) in which a second fuel supplied thereto by the fuel circuit (70) and the products of the combustion of the first fuel are combustible, a plurality of fuel injectors (60), which are structurally supported by the transition zone (43) and coupled to the fuel circuit (70), and which are configured to supply the second fuel to the second interior (41) in any one of a single axial stage, multiple axial stages, a single axial circumferential stage and multiple axial circumferential stages, and a control system coupled to the fuel circuit (70) and configured to control relative amounts of the first and second fuels supplied by the fuel circuit (70) to the first and second interiors (21, 41).

Late lean injection with adjustable air splits

A gas turbine engine is provided and includes a combustor having a first interior in which a first fuel is combustible, a turbine into which products of at least the combustion of the first fuel are receivable, a transition zone, including a second interior in which a second fuel and the products of the combustion of the first fuel are combustible, a plurality of fuel injectors which are configured to supply the second fuel to the second interior in any one of a single axial stage, multiple axial stages, a single axial circumferential stage and multiple axial circumferential stages, a compressor, by which air is supplied to the first and second interiors for the combustion therein, and a control system configured to control relative amounts of the air to the first and second interiors and relative amounts of the first and second fuels supplied to the first and second interiors.

Can to can modal decoupling using can-level fuel splits

In exemplary embodiments, a gas turbine system is provided. The gas turbine system can include a compressor configured to compress air and combustor cans in flow communication with the compressor, the combustor cans being configured to receive compressed air from the compressor and to combust a fuel stream. The gas turbine system can also include a multi-circuit manifold coupled to the combustor cans and configured to provide a split fuel stream from the fuel stream to the combustor cans.

Power generation system exhaust cooling

A turbomachine system according to an embodiment includes: a gas turbine system (12) including a compressor component (18), a combustor component (20), and a turbine component (22); a mixing area (33, 80) for receiving an exhaust gas stream (32) produced by the gas turbine system (12); a fluid injection system (60) for injecting a fluid into the mixing area (33, 80) to reduce a temperature of the exhaust gas stream (32); and an exhaust processing system (14) for processing the reduced temperature exhaust gas stream (32).

Methods and systems for controlling a combustor in turbine engines

Embodiments of methods and systems for controlling a combustor (104) for a turbine engine (100) are provided. According to one example embodiment, a system includes an air control assembly (406) associated with at least one air path of a combustor (104) for a turbine engine (100). Additionally, the system also includes at least one sensor (402) for sensing at least one operating parameter of the turbine engine (100). Further, the system also includes a controller (404) operable to receive at least one operating parameter sensed by the at least one sensor (402), and further operable to selectively control an air control assembly (406) based at least in part on the at least one operating parameter sensed by the at least one sensor (402).

Gas turbine engine combustor assembly having integrated control valves

A combustor assembly for a gas turbine engine includes a combustor endcover having at least one fuel circuit and mounted thereto a plurality of pre-mixers and at least one control valve. The at least one control valve is fluidly connected to the at least one fuel circuit and operatively connected to a controller. The controller selectively operates the at least one control valve to deliver fuel through the at least one fuel circuit to the plurality of pre-mixers in order to achieve an enhanced level of operational flexibility by providing individual combustion chamber control.

Optical sensors for combustion control

Certain embodiments of the invention may include systems and methods for providing optical sensors for combustion control. According to an example embodiment of the invention, a method for controlling combustion parameters associated with a gas turbine combustor is provided. The method can include providing at least one optical path adjacent to a flame region in the combustor, detecting at least a portion of the light emission from the flame region within the at least one optical path, and controlling at least one of the combustion parameters based in part on the detected light emission.

Systems and apparatus relating to downstream fuel and air injection in gas turbines

A gas turbine engine that includes: a combustor coupled to a turbine and a downstream injection system that includes two injection stages, a first stage and a second stage, positioned within an interior flowpath, wherein the first stage comprises an axial position that is aft of the primary air and fuel injection system and the second stage comprising an axial position that is aft of the first stage. Each of the first stage and the second stage include a plurality of circumferentially spaced injectors, each injector of which is configured to inject air and fuel into a flow through the interior flowpath. The first stage and the second stage have a configuration that limits a fuel injected at the second stage to less than 50% of a fuel injected at the first stage.

Control for enhanced performance of dln gas turbine

(57)【要約】 【課題】 本発明は、複数の燃焼チャンバを有する産業 用ガスタービンのための燃料調整システムに関する。 【解決手段】 多数の燃焼チャンバ（１６）のための多 数の燃料弁（６０）を有するガスタービンの制御システ ム及び方法は、該燃料弁（６０）を、関連する燃焼チャ ンバ（１６）に対して調整して、窒素酸化物エミッショ ン、動的圧力及び燃空比の変動を最適化することを含 む。さらに、燃料弁（６０）の微調整が次に用いられ て、動的圧力振動、窒素酸化物エミッション、又は燃空 比の変動を所定限界内に維持する。

Gas turbine combustor assembly with integrated control valves

Eine Brennkammeranordnung (8) für eine Gasturbine enthält eine Brennkammerendabdeckung (9) mit wenigstens einem Brennstoffkreis (42) und mehreren darauf montierten Vormischern (14-16) und wenigstens einem Regelventil (49). Das wenigstens eine Regelventil (49) ist fluidmäßig mit dem wenigstens einem Brennstoffkreis (42) und betrieblich mit einer Regelungseinrichtung (65) verbunden. Die Regelungseinrichtung (65) betreibt selektiv das wenigstens eine Regelventil (49), um Brennstoff über den wenigstens einen Brennstoffkreis (42) an die mehreren Vormischer (14-16) zu liefern, um einen verbesserten Grad von Betriebsflexibilität durch die Bereitstellung einer individuellen Brennkammer-Regelungseinrichtung zu erreichen. A combustor assembly (8) for a gas turbine includes a combustor end cover (9) having at least one fuel circuit (42) and a plurality of premixers (14-16) and at least one control valve (49) mounted thereon. The at least one control valve (49) is fluidly connected to the at least one fuel circuit (42) and operatively connected to a control device (65). The controller (65) selectively operates the at least one control valve (49) to supply fuel to the plurality of premixers (14-16) via the at least one fuel circuit (42) to provide an improved degree of operational flexibility through the provision of an individual combustor. To achieve regulation device.

Machine-specific probabilistic control in gas turbine tuning for power output-emissions parameters, related control systems, computer program products and methods

A system includes: a computing device configured to tune a set of gas turbines (GTs) by: commanding each GT to a base load level; commanding each GT to adjust a respective power output to match a nominal power output value, and subsequently measuring an actual emissions value for each GT; adjusting an operating condition of each GT based upon a difference between the respective measured actual emissions value and a nominal emissions value at the ambient condition; updating a pre-existing emissions model for each GT based upon the adjusted operating condition; running a set of operating conditions on each GT and measuring an updated emissions value; and refining the updated pre-existing emissions model based upon a difference between the updated emissions value and the updated pre-existing emissions model.

Systems and methods to improve shut-down purge flow in a gas turbine system

A system includes a controller including a memory storing instructions and a processor that executes the instructions. The instructions cause the controller to control a steam turbine system coupled to a power generation system to release steam during deceleration of a gas turbine. The instructions cause the controller to receive a first temperature of the gas turbine and a rotational speed of the gas turbine. The instructions cause the controller to calculate an exhaust flow rate of the power generation system based on at least the first input signal and the second input signal. The instructions cause the controller to control the power generation system to isolate a fuel source from the gas turbine at a portion of normal operating speed of the gas turbine sufficient to achieve a predetermined purging volume during coast down of air flow through the power generation system based on the exhaust flow rate.

Systems and methods for a fuel pressure oscillation device for reduction of coherence

A system with a gas turbine engine is provided. The gas turbine engine includes a first combustor comprising a first fuel nozzle, a second combustor comprising a second fuel nozzle, and a first fuel pressure oscillation system. The first fuel pressure oscillation system includes a first rotary device coupled to a first fuel circuit. The first fuel circuit is disposed along a first fuel passage leading to the first fuel nozzle. The first rotary device is configured to generate a first fuel pressure oscillation through the first fuel nozzle. The gas turbine engine also includes a second fuel pressure oscillation system having a second rotary device coupled to a second fuel circuit. The second fuel circuit is disposed along a second fuel passage leading to the second fuel nozzle, and the second rotary device is configured to generate a second fuel pressure oscillation through the second fuel nozzle.

Controllo probabilistico specifico per macchina in regolazione di turbine a gas per parametri di emissioni di uscita di potenza, relativi sistemi di controllo, prodotti di programmi informatici e metodi.

Machine-specific probabilistic control in gas turbine tuning for power output-emissions parameters, related control systems, computer program products and methods

A system includes: a computing device configured to tune a set of gas turbines (GTs) by: commanding each GT to a base load level; commanding each GT to adjust a respective power output to match a nominal power output value, and subsequently measuring an actual emissions value for each GT; adjusting an operating condition of each GT based upon a difference between the respective measured actual emissions value and a nominal emissions value at the ambient condition; updating a pre-existing emissions model for each GT based upon the adjusted operating condition; running a set of operating conditions on each GT and measuring an updated emissions value; and refining the updated pre-existing emissions model based upon a difference between the updated emissions value and the updated pre-existing emissions model.

Mehrfachrohrthermosicherung zum Schutz einer Düse vor einem Flammenhaltungs- oder Flammenrückschlagereignis

Schutzsystem für eine Düse (14) für ein Triebwerk (2), wobei das Schutzsystem aufweist:einen Grundkörper (44) mit einem Einlassabschnitt (46, 146), einem Auslassabschnitt (52, 152) und einer äußeren Wand (45, 145), die gemeinsam wenigstens einen Brennstoffzufuhrsammelraum (74, 76, 78; 161) bilden;mehrere Rohre (60, 160), die sich von dem Einlassabschnitt (46, 146) zu dem Auslassabschnitt (52, 152) des Grundkörpers (44, 145) durch wenigstens einen Teil des wenigstens einen Brennstoffzufuhrsammelraums (74, 76, 78; 161) erstrecken, wobei wenigstens eines der mehreren Rohre (60, 160) ein Brennstoff-Luft-Vormischrohr zur Vermischung von Brennstoff und Luft vor der Ausgabe durch den Auslassabschnitt (52, 152) ist, wobei das wenigstens eine Brennstoff-Luft-Vormischrohr wenigstens eine Brennstoffzufuhröffnung (103-105; 203) aufweist, die Brennstoff aus dem wenigstens einen Brennstoffzufuhrsammelraum (74, 76, 78; 161) in das wenigstens eine Brennstoff-Luft-Vormischrohr liefert; undwenigstens eine Thermosicherung (201, 211-213), die auf einer Außenfläche des wenigstens einen Brennstoff-Luft-Vormischrohres angeordnet ist, wobei die wenigstens eine Thermosicherung (201, 211-213) auf einem Material basiert, das ausgewählt ist, um auf eine Zündung eines Brennstoff-Luft-Gemisches in dem wenigstens einen Brennstoff-Luft-Vormischrohr hin zu schmelzen, und die wenigstens eine Thermosicherung (201, 211-213) angeordnet ist, um nach Schmelzen ein Umleiten von Brennstoff aus der Brennstoffzufuhröffnung (103-105; 203) zu wenigstens einer Bypassöffnung (205) stromabwärts der wenigstens einen Thermosicherung (201, 211-213) zu bewirken.

Systeme und Verfahren zur Verbesserung der Abschaltspülströmung in einem Gasturbinensystem

Ein System enthält eine Steuereinrichtung (36), die einen Speicher (38), der Instruktionen speichert, und einen Prozessor (42) enthält, der die Instruktionen ausführt. Die Instruktionen veranlassen die Steuereinrichtung (36), ein Dampfturbinensystem (128), das mit einem Energieerzeugungssystem gekoppelt ist, zu steuern, um während einer Verlangsamung einer Gasturbine (120) Dampf freizusetzen. Die Instruktionen veranlassen die Steuereinrichtung (36), eine erste Temperatur der Gasturbine (12) und eine Drehzahl der Gasturbine (12) zu empfangen. Die Instruktionen veranlassen die Steuereinrichtung (36), einen Abgasdurchsatz des Energieerzeugungssystems basierend auf wenigstens dem ersten Eingangssignal und dem zweiten Eingangssignal zu berechnen. Die Instruktionen veranlassen die Steuereinrichtung (36), das Energieerzeugungssystem zu steuern, um eine Brennstoffquelle von der Gasturbine (12) bei einem Anteil der normalen Betriebsdrehzahl der Gasturbine (12), der ausreicht, um ein vorbestimmtes Spülvolumen während eines Auslaufs einer Luftströmung durch das Energieerzeugungssystem zu erreichen, basierend auf dem Abgasdurchsatz zu trennen.

Integrierte Brennkammeranordnung und Erststufen-Leitdüse für eine Gasturbine und Verfahren

Eine integrierte Brennkammeranordnung und Erststufen-Leitdüse in einer Gasturbine weisen eine Brennkammer (22) auf, die vorgemischten Brennstoff und Luft aus wenigstens einer Brennstoff-Düsengruppe (24) in separaten Axialstellen aufnimmt. Die Brennkammer enthält ein Flammrohr (26) und ein Übergangsteil (28), die Heißbrenngas zu der Turbine leiten. Die Erststufen-Leitdüse (29), das Rohr (26) und das Übergangsteil (28) sind zu einem einzelnen Element integriert. Wenigstens eine der Axialstellen der einen oder mehreren Brennstoff-Düsengruppe weist mehrere Kleinmischvorrichtungen (30) auf, die Wärmefreisetzung konzentrieren und Flammenlänge vermindern.

Integrierte Brennkammeranordnung und Erststufen-Leitdüse für eine Gasturbine und Verfahren

Integrierte Rohr-Ring-Brennkammeranordnung und Erststufen-Leitdüse in einer Gasturbine mit einer Brennkammer (22), die an separaten Axialstellen vorgemischten Brennstoff und Luft aus wenigstens einer Brennstoff-Düsengruppe (24) aufnimmt, wobei die Brennkammer (22) ein Flammrohr (26) und ein Übergangsteil (28) enthält, die heißes Brenngas zu der Turbine leiten, wobei das Flammrohr (26), das Übergangsteil (28) und die Erststufen-Leitdüse (29) zu einem einzelnen Element integriert sind, wobei wenigstens eine der Axialstellen der einen oder mehreren Brennstoff-Düsengruppe (24) mehrere Mischvorrichtungen (30) aufweist, die dazu eingerichtet sind, die Wärmefreisetzung zu konzentrieren und die Flammenlänge zu vermindern.

Injector apparatus and reheat combustor

Aspects of the present disclosure provide an apparatus including: an injector in fluid communication with an aft section of a reheat combustor in a power generation system, the aft section being positioned downstream of a combustion reaction zone in the reheat combustor, and positioned upstream of a turbine stage of the power generation system, wherein the turbine stage includes a turbine nozzle and a turbine blade row; and a conduit in fluid communication with the injector, wherein the conduit delivers at least one of a fuel from a fuel supply line and a carrier gas to the injector.

Injektorvorrichtung mit Nachbrennkammer und Turbomaschine

Ausführungen der vorliegenden Offenbarung ergeben eine Vorrichtung, die aufweist: eine Reaktionskammer, die zwischen einer ersten Turbinenstufe eines Energieerzeugungssystems und einer nachfolgenden Turbinenstufe des Energieerzeugungssystems angeordnet ist, wobei die nachfolgende Turbinenstufe einen Turbinenleitapparat und eine Turbinenlaufschaufelreihe aufweist; mehrere Injektoren, die an einer Wand der Reaktionskammer angeordnet sind; und eine Leitung in Fluidverbindung mit den mehreren Injektoren aufweist, wobei die Leitung wenigstens eines von einem Brennstoff von einer Brennstoffzuführleitung und einem Trägergas zu der Reaktionskammer durch die mehreren Injektoren liefert.

燃料及びガス用の噴射システム

【課題】噴射システムは、燃料、空気、及び／又は不活性ガスを様々な方法で混合して、酸素と燃料が燃焼する前に混合させかつ混合物が燃焼チャンバを出る前に反応を完了させるための、様々な滞留期間をもたらすためのシステムを提供する。【解決手段】噴射システム５０は、発電システムの燃焼器と発電システムのタービン段とを分離するタービンノズル５４の表面に埋め込まれ、かつ、第１の出口６０と第２の出口６２の間に配置された混合ゾーンであって、第１の出口は第２の出口と概ね対向して配向される、混合ゾーン５２と、第１の出口を通してキャリアガスを混合ゾーンに送給するための第１の噴射導管６４と、第２の出口を通して燃料を混合ゾーンに送給するための第２の噴射導管６６を備え、キャリアガス及び燃料は、第１の噴射導管及び第２の噴射導管を出る際に混合ゾーンにおいて相互混合する。【選択図】図２

Einspritzsystem für Brennstoff und Trägergas.

Die vorliegende Erfindung stellt ein Einspritzsystem (50) für Brennstoff und Trägergas bereit. Das Einspritzsystem (50) weist auf: eine Mischzone (52), die in eine Oberfläche einer Turbinenleiteinrichtung (54) eingebettet und zwischen einem ersten Auslass (60) und einem zweiten Auslass (62) angeordnet ist, wobei die Turbinenleiteinrichtung (54) eine Brennkammer eines Energieerzeugungssystems von einer Turbinenstufe des Energieerzeugungssystems trennt, wobei der erste Auslass (60) im Wesentlichen entgegengesetzt zu dem ersten Auslass (62) ausgerichtet ist; einen ersten Einspritzkanal (64) zur Lieferung eines Trägergases zu der Mischzone (52) durch den ersten Auslass (60); einen zweiten Einspritzkanal (66) zur Lieferung eines Brennstoffes zu der Mischzone (52) durch einen zweiten Auslass (62); wobei sich das Trägergas und der Brennstoff innerhalb der Mischzone (52) nach dem Verlassen des ersten Einspritzkanals (64) und des zweiten Einspritzkanals (66) vermischen.

Injection systems for fuel and gas

Embodiments of the present disclosure provide injection systems for fuel and air. According to one embodiment, an injection system can include a mixing zone embedded within a surface of a turbine nozzle and positioned between a first outlet and a second outlet, the turbine nozzle separating a combustor of a power generation system from a turbine stage of the power generation system, wherein the first outlet is oriented substantially in opposition to the second outlet; a first injection conduit for delivering a carrier gas to the mixing zone through the first outlet; and a second injection conduit for delivering a fuel to the mixing zone through a second outlet; wherein the carrier gas and the fuel intermix within the mixing zone upon leaving the first injection conduit and the second injection conduit.

Vormischvorrichtung mit Schutzvorrichtung für ein Turbinen-Triebwerk und Verfahren zur Herstellung der Vormischvorrichtung.

Eine Vormischvorrichtung (14) für ein Turbinen(30)-Triebwerk (2) umfasst: einen Hauptkörper (44) mit einem Einlassabschnitt (46), einem Auslassabschnitt (52) und einer Aussenwand (45), die zusammen mindestens ein Brennstoffabgabeplenum bilden; und eine Vielzahl von Brennstoffmischröhren, die durch mindestens einen Abschnitt des mindestens einen Brennstoffabgabeplenums verlaufen, wobei jede von der Vielzahl von Brennstoffmischröhren mindestens eine Brennstoffzuleitungsöffnung aufweist, die mit dem mindestens einen Brennstoffabgabeplenum in Fluidverbindung steht; und eine Schutzvorrichtung, bestehend aus mindestens einer Thermosicherung (211), die auf einer Aussenfläche mindestens einer Brennstoffmischröhre (60) angeordnet ist, wobei die mindestens eine Thermosicherung (211) ein Material einschliesst, das bei einer Entzündung des Brennstoffs im Inneren der mindestens einen Brennstoffmischröhre (60) schmilzt und eine Umlenkung des Brennstoffs von der Brennstoffzuführungsöffnung zur mindestens einen Bypass-Öffnung bewirkt. Auch ein Verfahren zur Herstellung einer Vormischvorrichtung (14) mit der Schutzvorrichtung wird bereitgestellt.

System and method of cooling turbine airfoils with carbon dioxide

A turbine power generation system with enhanced cooling provided by a stream of carbon dioxide (46) from a carbon dioxide source (44) and a method of using a stream of carbon dioxide (46) to cool hot gas path components. The turbine power generating system includes a compressor (12), a combustor (66), a turbine (14), a generator (16), and at least one shaft (20) linking the compressor (12) and turbine (14) and generator (16) together such that mechanical energy produced from the turbine (14) is used to drive the compressor (12) and the generator (16). Carbon dioxide that is sequestered from the exhaust (26) of the turbine (14) may be stored and injected back into the turbine to cool hot gas path components of the turbine (14).

Optische Abfragesensoren zum Regeln/Steuern einer Verbrennung

Verfahren zum Regulieren von Verbrennungsparametern, die einer Gasturbinenbrennkammer (102) zugeordnet sind, wobei das Verfahren beinhaltet:Bereitstellen eines optischen Pfades (204), der durch die Gasturbinenbrennkammer (102) hindurchführt, wobei das Bereitstellen des optischen Pfades (204) ein Bereitstellen einer breitbandigen Lichtquelle (111) zur Erzeugung eines breitbandigen Lichts, eines optischen Eingabekanals (118), der in einem Körper der Gasturbinenbrennkammer (102) angeordnet ist, eines optischen Wellenleiters (114), der die Lichtquelle (111) mit dem optischen Eingabekanal (118) optisch verbindet, eines optischen Ausgabekanals (120), der in dem Körper der Gasturbinenbrennkammer (102) dem optischen Eingabekanal (118) gegenüberliegend angeordnet ist, einer Photodetektoranordnung (216) mit mehreren Photodetektoren (126), die mit dem optischen Ausgabekanal (120) über einen optische Ausgabepfad (204, 124, 215) optisch verbunden ist, und eines Übertragungssteuergitters (208) oder eines Reflexionssteuergitters (210), das stromaufwärts der Photodetektoranordnung (216) relativ zu der Lichtausbreitungsrichtung angeordnet ist, um dem Licht zugeordnete spektrale Informationen räumlich zu trennen;Fortleiten von Licht entlang des optischen Pfades (204), wobei das Fortleiten des Lichts entlang des optischen Pfades (204) ein Leiten des breitbandigen Lichts von der Lichtquelle (111) durch den optischen Wellenleiter (114) zu dem optischen Eingabekanal (118), Emittieren des breitbandigen Lichts aus dem optischen Eingabekanal (118) in die Gasturbinenbrennkammer (102) hinein, so dass das Licht sich durch einen freien Innenraum der Gasturbinenbrennkammer (102) ausbreitet, Empfangen des Lichts, das den freien Innenraum der Gasturbinenbrennkammer (102) durchquert hat, an dem optischen Ausgabekanal (120) und Weiterleiten des empfangenen Lichts entlang des optischen Ausgabepfads (204, 124, 215) zu der Photodetektoranordnung (216) aufweist, wobei das Übertragungssteuergitter (208) ...

Optische Sensoren zur Verbrennungssteuerung.

Bestimmte Ausführungsformen der Erfindung können Systeme und Verfahren zur Bereitstellung optischer Sensoren zur Verbrennungssteuerung beinhalten. Gemäss einer beispielhaften Ausführungsform der Erfindung ist ein Verfahren zum Steuern von Verbrennungsparametern, die mit einem Gasturbinenbrenner (102) in Verbindung stehen, geschaffen. Das Verfahren kann eine Bereitstellung wenigstens eines an einen Flammenbereich (106) in dem Brenner (102) angrenzenden optischen Pfades, eine Detektion wenigstens eines Teils der Lichtemission aus dem Flammenbereich (106) in dem wenigstens einen optischen Pfad und eine Steuerung von wenigstens einem der Verbrennungsparameter, basierend zum Teil auf der detektierten Lichtemission, beinhalten.

Optische Sensoren zur Verbrennungssteuerung

Bestimmte Ausführungsformen der Erfindung können Systeme und Verfahren zur Bereitstellung optischer Sensoren zur Verbrennungssteuerung beinhalten. Gemäß einer beispielhaften Ausführungsform der Erfindung ist ein Verfahren zum Steuern von Verbrennungsparametern, die mit einem Gasturbinenbrenner (102) in Verbindung stehen, geschaffen. Das Verfahren kann eine Bereitstellung wenigstens eines an einen Flammenbereich (106) in dem Brenner (102) angrenzenden optischen Pfades, eine Detektion wenigstens eines Teils der Lichtemission aus dem Flammenbereich (106) in dem wenigstens einen optischen Pfad und eine Steuerung von wenigstens einem der Verbrennungsparameter basierend zum Teil auf der detektierten Lichtemission beinhalten.

Brennkammerkonstruktion für Gasturbinenmotor.

Die Brennkammern einer Gasturbine besitzt einen Brennkammerdeckel (9) mit mindestens einem Kraftstoffanschluss (42) und mehreren auf dem Deckel montierten Vormischern (14-16) und mindestens einem Steuerventil (49). Das mindestens eine Steuerventil (49) steht in Fliessverbindung mit mindestens einem Kraftstoffanschluss (42) und in Arbeitsverbindung mit einer Steuerung (65). Die Steuerung (65) betätigt selektiv das mindestens eine Steuerventil (49) zur Abgabe von Kraftstoff durch den mindestens einen Kraftstoffanschluss (42) an die mehreren Vormischer (14-16), um ein erhöhtes Mass an Betriebsflexibilität durch eine individuelle Brennkammersteuerung zu erzielen.

An improved apparatus

Systems and methods to improve shut-down purge flow in a gas turbine system

A system includes a controller including a memory storing instructions and a processor that executes the instructions. The instructions cause the controller to receive a first input signal of a first temperature at an inlet of a gas turbine of a gas turbine and heat recovery steam generator (HRSG) system and a second input signal of a rotational speed of the gas turbine. The instructions also cause the controller to calculate the exhaust flow rate of the gas turbine and HRSG system based on the first input signal and the second input signal. Further, the instructions cause the controller to control the gas turbine and HRSG system to isolate a fuel source at a portion of normal operating speed of the gas turbine sufficient to achieve a predetermined purging volume during coast down of air flow through the gas turbine and HRSG system based on the exhaust flow rate.

Gasturbinensystem mit Mehrkreislaufverteiler zur Brennkammer-zu-Brennkammer-Modenentkopplung mittels Brennstoffaufteilungen auf Brennkammerrohrebene.

Gemäss einem Aspekt der Erfindung ist ein Gasturbinensystem (100) geschaffen. Das Gasturbinensystem (100) enthält einen Verdichter (110), der dazu eingerichtet ist, Luft zu verdichten (115) und Brennkammerrohre (120), die in Strömungsverbindung mit dem Verdichter (110) stehen, wobei die Brennkammerrohre (120) dazu eingerichtet sind, verdichtete Luft (115) aus dem Verdichter (110) aufzunehmen, und einen Brennstoffstrom zu verbrennen. Das Gasturbinensystem (100) enthält ferner einen Mehrkreislaufverteiler (200), der mit den Brennkammerrohren (120) verbunden ist und der dazu eingerichtet ist, anhand des Brennstoffstroms den Brennkammerrohren (120) einen aufgeteilten Brennstoffstrom zu liefern.

Gasturbinensystem mit Mehrkreislaufverteiler.

Das erfindungsgemässe Gasturbinensystem (100) enthält einen Verdichter (110), der dazu eingerichtet ist, Luft zu verdichten (115) und Brennkammerrohre (120), die in Strömungsverbindung mit dem Verdichter (110) stehen, wobei die Brennkammerrohre (120) dazu eingerichtet sind, verdichtete Luft (115) aus dem Verdichter (110) aufzunehmen, und einen Brennstoffstrom zu verbrennen. Das Gasturbinensystem (100) enthält ferner einen Mehrkreislaufverteiler (200), der mit den Brennkammerrohren (120) verbunden ist und der dazu eingerichtet ist, aus dem Brennstoffstrom den Brennkammerrohren (120) einen aufgeteilten Brennstoffstrom zu liefern.

System und Verfahren zur Isolierung von Turbinen und zugehörigen Rohrleitungen.

Ein Isoliersystem (1) enthält wenigstens einen Turbinenisolierraum (2), der konfiguriert ist, um wenigstens einen Teil einer Turbine zu umschliessen, einen Isolierungslagerraum (4), der konfiguriert ist, um einen Isolierungsvorrat aufzubewahren; mehrere erste Rohre (8, 10), die mit dem Turbinenisolierraum (2) und dem Isolierungslagerraum (4) verbunden sind, und ein Gebläse (6), das konfiguriert ist, um einen Luftstrom in wenigstens einem ersten Rohr zu erzeugen, um die Isolierung zwischen dem Isolierungslagerraum und dem wenigstens einen Turbinenisolierraum pneumatisch zu befördern. Ein Verfahren zum Isolieren wenigstens eines Teils einer Turbine enthält ein Einschliessen wenigstens eines Teils der Turbine in einem Raum und pneumatisches Zuführen der Isolierung in den Raum.

ガス・タービンの下流燃料及び空気噴射に関わるシステム及び装置

【課題】ガス・タービンにおいて、放出、特にＮＯｘの放出を減少させて、さらに高い発火温度を可能にする新規の燃焼システム設計を提供する。 【解決手段】共に内部流路を画定するタービンに結合された燃焼器であって、内部流路は、前端を画定する主空気及び燃料噴射システムから長手軸の周りに後方に、燃焼器がタービンに接続する境界面を通り、後端を画定するタービンの静翼列を通って延在している、燃焼器と、内部流路の長手軸に沿って軸方向に隔設された二つの噴射段すなわち第一段及び第二段を含んでいる下流噴射システムとを含んでいるガス・タービンである。第一段及び第二段は各々、混合気を内部流路に噴射するように構成されている多数の噴射器を含んでいる。 【選択図】図１９

Gasifier and cyclone separator for coal combustion

A direct-fired coal combustion system (100) includes a swirl chamber (114) having an input configured to receive a coal-water slurry and causing the coal-water slurry to mix with discharge air from a compressor (106) to gasify the coal-water slurry and create a synthesis gas. The system also includes a cyclone separator (116) directly coupled to the second end of the swirl chamber (114) and a second stage combustion input (112) coupled to an output of the cyclone separator.

Power generation system exhaust cooling

An airflow control system for a combined cycle power generation system according to an embodiment includes: a compressor component of a gas turbine system for generating an excess flow of air; a mixing area for receiving an exhaust gas stream produced by the gas turbine system; and an air extraction system for extracting at least a portion of the excess flow of air generated by the compressor component of the gas turbine system to provide bypass air, and for diverting the bypass air into the mixing area to reduce a temperature of the exhaust gas stream; wherein the reduced temperature exhaust gas stream is provided to a heat recovery steam generator.

Application of combined probabilistic control in gas turbine tuning for power output-emissions parameters with scaling factor, related control systems, computer program products and methods

Various embodiments include a system having: at least one computing device configured to tune a set of gas turbines (GTs) by performing actions including: commanding each GT in the set of GTs to a base load level, based upon a measured ambient condition for each GT; commanding each GT in the set of GTs to adjust a respective power output to match a scaled power output value equal to a fraction of a difference between the respective power output and a nominal power output value, and measuring an actual emissions value for each GT during the adjusting of the respective power output; and adjusting an operating condition of each GT in the set of GTs based upon a difference between the respective measured actual emissions value, a nominal emissions value at the ambient condition and a nominal emissions value at the ambient condition.

Machine-specific combined probabilistic control in gas turbine tuning for power output-emissions parameters with scaling factor, related control systems, computer program products and methods

Commanding GTs to base load level based upon measured ambient condition for each GT; commanding each GT to adjust a power output to match scaled power output value equal to a fraction of a difference between the respective power output and a nominal power output value, and measuring actual emissions value for each GT during the adjusting of the respective power output; adjusting operating condition of each GT based upon a difference between the respective measured actual emissions value, a nominal emissions value at the ambient condition and emissions scale factor; updating a pre-existing emissions model for each GT based upon the adjusted operating; running set of operating conditions on each GT and measuring updated parameters for each GT including an updated emissions value; and refining updated pre-existing emissions model based upon a difference between the updated emissions value and the updated pre-existing emissions model.

Application of combined probabilistic control in gas turbine tuning for power output-emissions parameters with scaling factor, related control systems, computer program products and methods

Various embodiments include a system having: at least one computing device configured to tune a set of gas turbines (GTs) by performing actions including: commanding each GT in the set of GTs to a base load level, based upon a measured ambient condition for each GT; commanding each GT in the set of GTs to adjust a respective power output to match a scaled power output value equal to a fraction of a difference between the respective power output and a nominal power output value, and modeling an emissions value for the GT during the adjusting of the respective power output; and adjusting an operating condition of each GT in the set of GTs based upon a difference between the respective modelled emissions value, a nominal emissions value at the ambient condition and a nominal emissions value at the ambient condition.

Combined probabilistic control in gas turbine tuning for power output-emissions parameters with scaling factor, related control systems, computer program products and methods

Commanding GTs to base load level based upon measured ambient condition for each GT; commanding each GT to adjust a power output to match scaled power output value equal to a fraction of a difference between the respective power output and a nominal power output value, and measuring actual emissions value for each GT during the adjusting of the respective power output; and adjusting an operating condition of each GT in the set of GTs based upon a difference between the respective measured actual emissions value, a nominal emissions value at the ambient condition and an emissions scale factor, wherein the nominal emissions value at the ambient condition and the emissions scale factor are stored in a pre-existing emissions model for the GT.

Application of probabilistic control in gas turbine tuning for power output-emissions parameters with scaling factor, related control systems, computer program products and methods

Various embodiments include a system having: at least one computing device configured to tune a set of gas turbines (GTs) by performing actions including: commanding each GT in the set of GTs to a base load level, based upon a measured ambient condition for each GT; commanding each GT in the set of GTs to adjust a respective power output to match a scaled power output value equal to a fraction of a difference between the respective power output and a nominal power output value, and subsequently measuring an actual emissions value for each GT; and adjusting an operating condition of each GT in the set of GTs based upon a difference between the respective measured actual emissions value, a nominal emissions value at the ambient condition and a nominal emissions value at the ambient condition.

Power generation system exhaust cooling

A turbomachine system according to an embodiment includes: a gas turbine system including a compressor component, a combustor component, and a turbine component; a mixing area for receiving an exhaust gas stream produced by the gas turbine system; a fluid injection system for injecting a fluid into the mixing area to reduce a temperature of the exhaust gas stream; and an exhaust processing system for processing the reduced temperature exhaust gas stream.

Power generation system exhaust cooling

An airflow control system for a gas turbine system according to an embodiment includes: a compressor component of a gas turbine system; a mixing area for receiving an exhaust gas stream produced by the gas turbine system; an air extraction system for extracting a supply of bypass air from an excess flow of air generated by the compressor component of the gas turbine system; an enclosure surrounding the gas turbine system and forming an air passage, the bypass air flowing through the air passage and around the gas turbine system into the mixing area to reduce a temperature of the exhaust gas stream; and an exhaust processing system for processing the reduced temperature exhaust gas stream.

Power generation system exhaust cooling

A power generation system according to an embodiment includes: a gas turbine system including a compressor component, a combustor component, and a turbine component; an airflow generation system coupled to an expander shaft downstream of the gas turbine system for drawing in a flow of ambient air through an air intake section; a mixing area for receiving an exhaust gas stream produced by the gas turbine system; a flow directing system for directing the flow of ambient air generated by the airflow generation system to the mixing area to reduce a temperature of the exhaust gas stream; and an exhaust processing system for processing the reduced temperature exhaust gas stream.

Integrated combustor and stage 1 nozzle in a gas turbine and method

An integrated combustor and stage one nozzle in a gas turbine includes a combustion chamber that receives premixed fuel and air from at least one fuel nozzle group at separate axial locations. The combustion chamber includes a liner and a transition piece that deliver hot combustion gas to the turbine. The stage one nozzle, the liner and the transition piece are integrated into a single part. At least one of the axial locations of the one or more fuel nozzle groups includes a plurality of small scale mixing devices that concentrate heat release and reduce flame length.

Power output and emissions based degraded gas turbine tuning and control systems, computer program products and related methods

Various embodiments include a system having: at least one computing device configured to tune a set of gas turbines (GTs) by performing actions including: commanding each GT in the set of GTs to a base load level, based upon a measured ambient condition for each GT; commanding each GT in the set of GTs to adjust a respective output to match a nominal mega-watt power output value, and subsequently measuring an actual emissions value for each GT; adjusting an operating condition of each GT in the set of GTs based upon a difference between the respective measured actual emissions value and a nominal emissions value at the ambient condition; and calculating a degradation for each GT in the set of GTs over a period.

Probabilistic control in gas turbine tuning for power output-emissions parameters, related control systems, computer program products and methods

Various embodiments include a system having: at least one computing device configured to tune a set of gas turbines (GTs) by performing actions including: commanding each GT in the set of GTs to a base load level, based upon a measured ambient condition for each GT; commanding each GT in the set of GTs to adjust a respective power output to match a nominal power output value, and subsequently measuring an actual emissions value for each GT; adjusting an operating condition of each GT in the set of GTs based upon a difference between the respective measured actual emissions value and a nominal emissions value at the ambient condition; and setting a target operating condition for each GT to match the adjusted operating condition after the adjusting of the operating condition.

Modelling probabilistic control in gas turbine tuning for power output-emissions parameters, related control systems, computer program products and methods

Various embodiments include a system having: at least one computing device configured to tune a set of gas turbines (GTs) by performing actions including: commanding each GT in the set of GTs to a base load level, based upon a measured ambient condition for each GT; commanding each GT in the set of GTs to adjust a respective power output to match a nominal power output value, and subsequently measuring an actual emissions value for each GT; adjusting an operating condition of each GT in the set of GTs based upon a difference between the respective measured actual emissions value and a nominal emissions value at the ambient condition; and building an independent emissions model for each GT based upon the measured actual emissions value for each GT and the adjusted operating condition of each GT.

Power outlet, emissions, fuel flow and water flow based probabilistic control in liquid-fueled gas turbine tuning, related control systems, computer program products and methods

Various embodiments include a system having: at least one computing device configured to tune a set of gas turbines (GTs) by performing actions including: commanding each GT in the set of GTs to a base load level, based upon a measured ambient condition for each GT; commanding each GT in the set of GTs to adjust a respective output to match a nominal mega-watt power output value, and subsequently measuring an actual fuel flow value and an actual emissions value for each GT; adjusting at least one of a fuel flow or a water flow for each GT to an adjusted water/fuel ratio in response to the actual emissions value deviating from an emissions level associated with the base load level, while maintaining the respective adjusted output; and adjusting an operating condition of each GT in the set of GTs based upon a difference between the respective measured actual fuel flow value and a nominal fuel flow value at the ambient condition, while maintaining the adjusted water/fuel ratio.